US4430890A
Expired / Lapsed
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Two layer hydraulic analogy method for testing supersonic gas flows with shock waves
Assignee: United States Department of the Navy
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Filing: 1982-05-14
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Granted: 1984-02-14
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Expires: 2002-05-14
Abstract
Abstract A method of studying steady and unsteady supersonic gas flow using a two layer hydraulic analogy technique. The method simulates the specific heat ratio of the gas. Two layers of immiscible liquids having different densities and thicknesses are held in a shallow container. The densities are chosen and the layer thicknesses are adjusted to simulate the specific heat ratio of the gas. A model of a device to be studied is submerged in the liquid. Relative flow is caused to occur between the model and liquid simulating steady flow. The depth of the lower layer during the period of relative flow is measured and is analogous to steady state gas flow characteristics. For studying unsteady flow two bodies of liquids each having two layers of liquids of densities chosen, and lower layer thicknesses adjusted to simulate the specific heat ratio of the gas and to simulate a high and low pressure across a gas system, are held in a container separated by a removable gate. Flow is caused to occur from the high to low pressure liquid body simulating unsteady flow. The depth of the lower layers during the period of flow is analogous to unsteady gas flow characteristics.
Inventors
- 👤 Franklin D. Hains
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 16:03
CPC Classifications
G; G01; G01M; G01M10/00; G01M9/00; G01M9/06; G01M9/065
Claims Analysis
Total Claims: 16
Claim 1
Independent Claim
187 words
A method of studying steady state supersonic gas flow characteristics at desired locations by simulating the specific heat ratio of the gas and the Mach number of the supersonic flow, the steps comprising: providing for a container having a flat bottom; establishing in the container a body of liquid having a lower layer of a liquid of depth H 2 and density D 2 resting on the container bottom and further having an upper layer of a liquid of depth H 1 and density D 1 less than said lower layer density floating on said lower layer for simulating the specific heat ratio of the gas, said layers form an interface therebetween; providing for a cross-sectional model submerged in said liquid body, said model rests on the container bottom and extends through said interface terminating within the upper layer; causing relative flow between the model and the body of liquid for simulating the Mach number of said gas flow; measuring the depth of the lower layer at said locations to be studied while said relative flow takes place, said measurements being analogous to supersonic gas flow characteristics.
Claim 2
Independent Claim
187 words
A method of studying steady state supersonic gas flow characteristics at desired locations by simulating the specific heat ratio of the gas and the Mach number of the supersonic flow, the steps comprising: providing for a container having a flat bottom; establishing in the container a body of liquid having a lower layer of a liquid of depth H 2 and density D 2 resting on the container bottom and further having an upper layer of a liquid of depth H 1 and density D 1 less than said lower layer density floating on said lower layer for simulating the specific heat ratio of the gas, said layers form an interface therebetween; providing for a cross-sectional model submerged in said liquid body, said model rests on the container bottom and extends through said interface terminating within the upper layer; causing relative flow between the model and the body of liquid for simulating the Mach number of said gas flow; measuring the depth of the lower layer at said locations to be studied while said relative flow takes place, said measurements being analogous to supersonic gas flow characteristics.
Claim 3
Dependent Claim
14 words
The method as defined in claim 1 wherein the lower layer liquid is mercury.
Claim 4
Dependent Claim
15 words
The method as defined in claim 1 wherein the upper layer liquid is methyl alcohol.
Claim 5
Dependent Claim
15 words
The method as defined in claim 1 wherein the upper layer liquid is ethyl alcohol.
Claim 6
Dependent Claim
14 words
The method as defined in claim 1 wherein the upper layer liquid is turpentine.
Claim 7
Dependent Claim
61 words
The method as defined in claim 1 wherein the upper layer thickness is determined according to the equation ##EQU6## where H 1 is the upper layer thickness, H 2 is the lower layer thickness, D 1 and D 2 are the densities of the upper and lower liquids, and γ is the specific heat ratio of the gas to be simulated.
Claim 8
Dependent Claim
63 words
The method as defined in claim 1 wherein the relative flow is determined according to the equation, ##EQU7## where V is the speed of relative flow, M is the Mach number to be simulated, g is the gravitational constant and D 1 and D 2 are the densities of the upper and lower liquids, and H 2 is the thickness of lower layer.
Claim 9
Independent Claim
298 words
A method of studying unsteady supersonic gas flow characteristics at desired locations by simulating the specific heat ratio of the gas and the pressure ratio across the gas flow system being studied the steps comprising: providing for a container having a flat bottom and further having means for dividing said container into a low pressure container side and a high pressure container side, said flat bottom forms the bottom of each of said container sides; establishing a body of liquid in said low pressure container side having a lower layer of a liquid of depth H 2 and density D 2 resting on said container bottom, and further having an upper layer of a liquid of depth H 1 and density D 1 less than said lower layer density floating on said lower layer for simulating the specific heat ratio of the gas said layers form an interface therebetween; establishing a body of liquid in said high pressure container side having a lower layer of the same liquid as said lower layer in the low pressure container side having a thickness H 4 resting on the container bottom and further having an upper layer of the same liquid as the upper layer in the low pressure container side of thickness H 3 floating on said high pressure container lower layer, the high pressure container lower layer thickness and the low pressure lower layer thicknesses adjusted to simulate said pressure ratio; causing flow to occur from the high pressure container side to the low pressure container side, said flow simulates the unsteady supersonic gas flow to be studied; measuring the depth of the lower layers at the desired locations to be studied while the flow takes place, said lower layer depth measurements being analogous to supersonic gas flow characteristics.
Claim 10
Independent Claim
298 words
A method of studying unsteady supersonic gas flow characteristics at desired locations by simulating the specific heat ratio of the gas and the pressure ratio across the gas flow system being studied the steps comprising: providing for a container having a flat bottom and further having means for dividing said container into a low pressure container side and a high pressure container side, said flat bottom forms the bottom of each of said container sides; establishing a body of liquid in said low pressure container side having a lower layer of a liquid of depth H 2 and density D 2 resting on said container bottom, and further having an upper layer of a liquid of depth H 1 and density D 1 less than said lower layer density floating on said lower layer for simulating the specific heat ratio of the gas said layers form an interface therebetween; establishing a body of liquid in said high pressure container side having a lower layer of the same liquid as said lower layer in the low pressure container side having a thickness H 4 resting on the container bottom and further having an upper layer of the same liquid as the upper layer in the low pressure container side of thickness H 3 floating on said high pressure container lower layer, the high pressure container lower layer thickness and the low pressure lower layer thicknesses adjusted to simulate said pressure ratio; causing flow to occur from the high pressure container side to the low pressure container side, said flow simulates the unsteady supersonic gas flow to be studied; measuring the depth of the lower layers at the desired locations to be studied while the flow takes place, said lower layer depth measurements being analogous to supersonic gas flow characteristics.
Claim 11
Dependent Claim
22 words
The method as defined in claim 8 wherein the lower layer liquid in the low and high pressure side containers is mercury.
Claim 12
Dependent Claim
23 words
The method as defined in claim 8 wherein the upper layer liquid in the low and high pressure side containers is methyl alcohol.
Claim 13
Dependent Claim
23 words
The method as defined in claim 8 wherein the upper layer liquid in the low and high pressure side containers is ethyl alcohol.
Claim 14
Dependent Claim
22 words
The method as defined in claim 8 wherein the upper layer liquid in the low and high pressure side containers is turpentine.
Claim 15
Dependent Claim
86 words
The method as defined in claim 8 wherein the thickness of the upper layer in the low pressure side container is determined according to the equation: ##EQU8## where H 1 is the thickness of the upper layer on the low pressure side container, H 2 is the thickness of the lower layer in the low pressure side container, D 1 and D 2 are the densities of the upper and lower layer liquids, and γ is the specific heat ratio of the gas to be simulated.
Claim 16
Dependent Claim
74 words
The method as defined in claim 8 wherein the thickness of the lower layer in the high pressure side container is determined according to the equation: H.sub.4 =H.sub.2 P.sub.2 /P.sub.1 where H 4 is the thickness of the lower layer in the high pressure container side, H 2 is the thickness of the lower layer in the low pressure container side, and (P 2 /P 1 ) is the pressure ratio to be simulated.
References Cited (Backward Citations)
No citation records indexed.
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1987-02-13 | 1987-08-15 | 1988-02-14 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-02-13 | 1991-08-15 | 1992-02-14 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-02-13 | 1995-08-15 | 1996-02-14 | $7700.00 | Window Closed / Lapsed |